CN106481459B

CN106481459B - Variablepiston fan pitch range limiter

Info

Publication number: CN106481459B
Application number: CN201610743520.0A
Authority: CN
Inventors: D.A.尼尔加思; B.W.米勒
Original assignee: General Electric Co
Current assignee: General Electric Co
Priority date: 2015-08-28
Filing date: 2016-08-29
Publication date: 2018-03-30
Anticipated expiration: 2036-08-29
Also published as: CN106481459A; EP3135922A1; US10443412B2; EP3135922B1; US20170058683A1; JP2017048785A; BR102016019793A2; CA2939739A1

Abstract

Variablepiston fan (38) for gas-turbine unit is provided.The variablepiston fan includes multiple fan blade (40) and actuating assembly, and the plurality of fan blade is rotatably coupled to disk (42), and the actuating assembly is used to change each pitch in multiple fan blade.The actuating assembly generally includes actuation component and pin (142), and the actuation component is operably connected at least one in multiple fan blade.The pin can be moved between the first position and the second position, and in the first position, the pin is positioned at least partially in the path (136) being limited in actuation component.When in said first position, the pin stops that actuation component exceeds the movement of the scope limited by path relative to pin.Actuating assembly also includes retraction system, and the retraction system is used to be selectively engaged pin when pin is moved into the second place from first position.

Description

Variablepiston fan pitch range limiter

Technical field

This theme relates generally to the variablepiston fan for gas-turbine unit, or more specifically, is related to tool There is the variablepiston fan for gas-turbine unit of pitch range limiter.

Background technology

Gas-turbine unit generally includes and flowed communication with one another the fan and core of arrangement.In addition, gas turbine The core of engine includes compressor section, burning block, turbine and exhaust area generally in a manner of flowing successively Section.In operation, air stream is provided to the import of compressor section from fan, here, one or more axial compressors Little by little compressed air, until it reaches burning block.Fuel is mixed and burnt with compressed air in burning block, to provide Burning gases.Burning gases are sent to turbine from burning block.Burning gases stream through turbine drives compression Machine section, and then pass through exhaust section and be for example sent to air.In specific configuration, turbine is by along gas turbine Engine axial direction extension one or more axles and be mechanically coupled to compressor section.

The fan includes multiple blades, and the plurality of blade has the radius bigger than the core of gas-turbine unit.The wind Fan and multiple blades are also mechanically connected in one in one or more axles so that they are rotated together with turbine.It is more Thrust of the rotation generation of individual blade for gas-turbine unit, and provide air stream to the compressor section of core.

For at least some gas-turbine units, the fan is variablepiston fan.By around corresponding oar Pitch away from axis rotating vane change fan blade is probably in accordance with need further to improve the performance of gas-turbine unit Want.For example, the first cause for changing blade pitch is the power of present air speed based on aircraft and engine The angle of attack of Level tune blade is for optimum performance.Alternatively, the pitch of fan blade can be used for making air reverse, so that around Cross the core of engine, therefore aircraft of the deboost with air force in braked landing is provided.

Generally by with multiple fan blade are operable connect in a manner of actuation component is provided, to change the plurality of fan blade Pitch.Actuation component can be energized for example, by hydraulic pressure or power driven system.If the however, power system event of actuation component Hinder, then multiple fan blade may be rotated to the pitch model of generation deboost from for generating the pitch range of forward thrust Enclose.If this occurs during flight forward, can damage.

Therefore, following actuation component will be useful that the actuation component has one or more peaces in correct position Full mechanism, with prevent multiple fan blade in system fault event from for generate the pitch range of forward thrust rotate to In the pitch range of production deboost.More specifically, following actuation component will be it is particularly advantageous that the actuation component has In one or more release mechanisms of correct position, to prevent multiple fan blade from the pitch model for generating forward thrust Spinning goes to the pitch range for generating deboost, and it can independently prevent such a rotation with the power system of actuation component Turn.

The content of the invention

Aspects and advantages of the present invention will be illustrated partly in the following description, or can become obvious from description, or be passed through The present invention implementation and acquistion.

In an example embodiment of the disclosure, there is provided the variablepiston fan for gas-turbine unit.This can Feather fan includes multiple fan blade, and the fan blade is rotatably coupled to disk, each limit in multiple fan blade Fixed pitch.The variablepiston fan also includes actuating assembly, and the actuating assembly is each in multiple fan blade for changing Pitch.The actuating assembly includes actuation component and pin, and the actuation component is operably connected in multiple fan blade at least One and restriction path.The pin can move between the first position and the second position, in the first position, the pin at least portion It is positioned in the path being limited in actuation component with dividing.When in said first position, the pin stops actuation component relative to pin Beyond the movement of the scope limited by path.Actuation component also includes retraction system, and the retraction system is used to be selectively engaged Pin, and the pin is moved to the second place from first position.

In another example embodiment of the disclosure, there is provided the variablepiston fan for gas-turbine unit.This can Feather fan includes being rotatably coupled to multiple fan blade of disk, the oar of each restriction first in the plurality of fan blade Away from scope and the second pitch range.The variablepiston fan also includes actuating assembly, and the actuating assembly is used to change multiple fans The pitch of blade.The actuating assembly includes actuation component, and the actuation component is operably connected in multiple fan blade extremely It is few one.The actuation component limits corresponding with the first pitch range the first range of movement and corresponding with the second pitch range the Two range of movement.The actuation component further defines path.The actuation component also includes pin, and the pin can be in first position and second Moved between putting, in the first position, the pin is positioned at least partially in the path being limited in actuation component.When the pin During in first position, the pin stops that actuation component leaves the second range of movement.Actuation component also includes retraction system, the retraction System is used to be selectively engaged pin, and the pin is moved to the second place from first position.

Technical scheme 1：A kind of variablepiston fan for gas-turbine unit, the variablepiston fan include：

Multiple fan blade, it is rotatably coupled to disk, each restriction pitch in the multiple fan blade；With

Actuating assembly, it is used to change each pitch in the multiple fan blade, and the actuating assembly includes：

Actuation component, it is operably connected at least one and restriction path in the multiple fan blade；With

Pin, it can be moved between the first location and the second location, and in the first position, the pin is at least partly Ground is positioned in the path being limited in the actuation component, and the pin stops the rush when in the first position Dynamic component exceeds the movement of the scope limited by the path relative to the pin；With

Retraction system, it is used to be selectively engaged the pin and the pin is moved to described from the first position Two positions.

Technical scheme 2：Variablepiston fan according to technical scheme 1, wherein, the actuation component is can be relative In the grooming ring of the disc spins.

Technical scheme 3：Variablepiston fan according to technical scheme 2, wherein, the grooming ring limits multiple grooves Road, wherein, the actuating assembly also includes multiple chain arms, wherein, each chain arm is operatively coupled to the multiple fan leaf One in piece and be connected in the multiple conduit limited by the grooming ring one.

Technical scheme 4：Variablepiston fan according to technical scheme 2, wherein, the institute being limited in the grooming ring Stating path, generally circumferentially direction extends.

Technical scheme 5：Variablepiston fan according to technical scheme 1, wherein, the path limit length, wherein, The length of the path represents the first pitch range of the multiple fan blade.

Technical scheme 6：Variablepiston fan according to technical scheme 5, wherein, the multiple fan blade further defines Second pitch range, wherein, when the pin is in the second place, the actuation component limits the length than the path The big range of movement relative to the pin, and wherein, the range of movement of the increase of the actuation component is corresponding to the multiple Second pitch range of fan blade.

Technical scheme 7：Variablepiston fan according to technical scheme 1, wherein, the actuating assembly also includes pin master Body, wherein, the pin can move between the first position and the second place relative to the pin main body.

Technical scheme 8：Variablepiston fan according to technical scheme 7, wherein, the pin in the first position and It is moved linearly by between the second place relative to the pin main body.

Technical scheme 9：Variablepiston fan according to technical scheme 7, wherein, the retraction system is hydraulic retraction System, the hydraulic retraction system optionally make the pin be moved to the second place using hydraulic pressure.

Technical scheme 10：Variablepiston fan according to technical scheme 7, wherein, the multiple fan blade can Rotated by fan shaft, and wherein, the pin main body is fixed relative to the fan shaft.

Technical scheme 11：Variablepiston fan according to technical scheme 1, wherein, the actuation component is chain arm, Wherein, the actuating assembly also includes multiple chain arms, and wherein, each chain arm is operatively coupled to the multiple fan leaf One in piece.

Technical scheme 12：A kind of variablepiston fan for gas-turbine unit, the variablepiston fan include：

Multiple fan blade, it is rotatably coupled to disk, the pitch of each restriction first in the multiple fan blade Scope and the second pitch range；With

Actuating assembly, it is used for the pitch for changing the multiple fan blade, and the actuating assembly includes：

Actuation component, it is operably connected at least one in the multiple fan blade, the actuation component limit Fixed the first range of movement corresponding with first pitch range and the second range of movement corresponding with the second pitch range, it is described Actuation component further defines path；With

Pin, it can be moved between the first position and the second position, and in the first position, the pin is at least partly Ground is positioned in the path being limited in the actuation component, when the pin is in the first position, the pin resistance Keep off the actuation component and leave second range of movement；With

Technical scheme 13：Variablepiston fan according to technical scheme 12, wherein, the first fortune of the actuation component Dynamic scope is the first range of movement relative to the disk, and wherein, the second range of movement of the actuation component be relative to Second range of movement of the disk.

Technical scheme 14：Variablepiston fan according to technical scheme 12, wherein, the actuation component is being capable of phase For the grooming ring of the disc spins.

Technical scheme 15：Variablepiston fan according to technical scheme 14, wherein, the grooming ring limits multiple grooves Road, wherein, the actuating assembly also includes multiple chain arms, wherein, each chain arm is operatively coupled to the multiple fan leaf One in piece and be connected in the multiple conduit limited by the grooming ring one.

Technical scheme 16：Variablepiston fan according to technical scheme 14, wherein, it is limited in the grooming ring Generally circumferentially direction extends the path.

Technical scheme 17：Variablepiston fan according to technical scheme 12, wherein, the path limit length, its In, the length of the path represents the first range of movement of the actuation component.

Technical scheme 18：Variablepiston fan according to technical scheme 12, wherein, the actuating assembly also includes pin Main body, wherein, the pin can move between the first position and the second place relative to the pin main body.

Technical scheme 19：Variablepiston fan according to technical scheme 18, wherein, the pin is in the first position It is moved linearly by between the second place relative to the pin main body.

Technical scheme 20：Variablepiston fan according to technical scheme 18, wherein, the retraction system is hydraulic compression The system of returning, the hydraulic retraction system optionally make the pin be moved to the second place using hydraulic pressure.

With reference to description below and appended claims, these and other features, aspect and advantage of the invention will become It is best understood from.It is incorporated to this specification and the part thereof of accompanying drawing of composition exemplifies embodiments of the invention, and is reinstated with explanation one To explain the principle of the present invention.

Brief description of the drawings

Of the invention complete including its optimal mode and come into force it is open for those skilled in the art referring to the drawings It is suggested in specification, in the figure：

Fig. 1 is the schematic section according to the gas-turbine unit of the example embodiment of this theme；

Fig. 2 is the past elevation backwards of the fan illustrated in Fig. 1 according to the example embodiment of the disclosure.

Fig. 3 is the longitudinal section view of the fan blade for the demonstration fan described in the Fig. 2 for limit the first pitch angle.

Fig. 4 is the longitudinal section view of the fan blade for the demonstration fan described in the Fig. 2 for limit the second pitch angle.

Fig. 5 is the longitudinal section view of the fan blade for the demonstration fan described in the Fig. 2 for limit the 3rd pitch angle.

Fig. 6 is the diagrammatic side view of the actuating assembly of Fig. 2 exemplary variable pitch fan, and wherein fan blade is in first Position.

Fig. 7 is the diagrammatic side view of the actuating assembly of Fig. 2 exemplary variable pitch fan, and wherein fan blade is in second Position.

Fig. 8 is according to the sectional view of the pin assemblies of the example embodiment of the disclosure, and the example embodiment can merge in figure 6 In the actuating assembly of description.

Fig. 9 is according to the sectional view of the pin assemblies of the example embodiment of the disclosure, and the example embodiment can merge in the figure 7 In the actuating assembly of description.

Figure 10 is the diagrammatic side view of the demonstration actuating assembly of Fig. 2 exemplary variable pitch fan, wherein at fan blade In the 3rd position.

Figure 11 is according to the sectional view of the pin assemblies of the example embodiment of the disclosure, and the example embodiment can merge in Figure 10 In the actuating assembly of middle description.

Figure 12 is the signal of the actuating assembly of Fig. 2 exemplary variable pitch fan, sectional view.

The reuse of reference symbol in the specification and drawings is intended to indicate the same or analogous feature of the present invention Or element.

List of parts

10 turbofans

12 longitudinally or axially center lines

14 fan sections

16 core turbogenerators

18 shell bodies

20 imports

22 low pressure compressors

24 high pressure compressors

26 burning blocks

28 high-pressure turbines

30 low-pressure turbines

32 jet-propelled exhaust sections

34 high-pressure shafts/rotating shaft

36 low-pressure shafts/rotating shaft

38 fans

40 blades

42 disks

44 leading edges

46 tips

48 actuating assemblies

50 power gear-boxes

52 rotatable hubs

54 blower-castings or cabin

56 export orientation stator blades

58 downstream sections

60 bypath air circulation roads

62 air

64 imports

The Part I of 66 air

The Part II of 68 air

70 burning gases

72 stator stator blades

74 turbine rotor blades

76 stator stator blades

78 turbine rotor blades

80 jet spray nozzles are vented

82 fan nozzle exhaust sections

84 hot gas paths

100 on the pressure side

102 suction sides

104 leading edges

105 chord lines

106 trailing edges

Root end in 108

110 distal tips

112 pitch angles

114 direction of rotation

116 forward thrusts

118 deboosts

120 fan shafts

122 grooming rings (scheduling ring)

124 chain arms

126 electro-motors

The first end of 128 chain arms

The second end of 130 chain arms

132 conduits

134 slide units

136 paths

138 path-lengths

140 pin assemblies

142 pins

144 pin main bodys

146 retraction systems

148 top chambers

150 hydraulic fluid circuits

The annular flange of 152 pins.

Embodiment

The existing embodiment of the present invention will be referred in detail now, illustrate the one or more of its in the accompanying drawings Example.It is described in detail using numeral and alphabetical designation to mean the feature in accompanying drawing.Class is used in accompanying drawing and the content of the invention Like or similar label come refer to the present invention similar or like part.As used in this article, term " first ", " Two " and " the 3rd " can be interchangeably used for distinguishing a component with another, and be not intended to represent the field of independent component Institute or importance.Term " upstream " and " downstream " refer to the relative direction relative to the fluid stream in fluid path.For example, " upstream " Refer to fluid from the direction that it flows, and " downstream " refers to the fluid stream and flow to its direction.However, it should be understood that herein The middle term " fluid " used includes any material or medium of flowing, including but not limited to gas and air.

With reference now to accompanying drawing, wherein, through accompanying drawing, identical label instruction similar elements, Fig. 1 is showing according to the disclosure The schematic section of the gas-turbine unit of model embodiment.More particularly, for Fig. 1 embodiment, gas turbine starts Machine is high bypassed turbine fan jet engine 10, herein referred to as " turbofan 10 ".As shown in FIG. 1, Turbofan 10 limits (longitudinal centre line 12 with being provided for reference extends parallel to) axial direction A, footpath To direction R and circumferential direction C (see Fig. 2).In general, turbofan 10 includes fan section 14 and configuration in fan section 14 The core turbogenerator 16 in downstream.

The demonstration core 16 of the turbogenerator 10 of description generally includes substantially tubular shape shell body 18, and it limits ring Shape import 20.Shell body 18 is surrounded with the relation flowed successively：Compressor section, it includes supercharger or low pressure (LP) compressor 22 and high pressure (HP) compressor 24；Burning block 26；Turbine, it includes high pressure (HP) turbine 28 and low pressure (LP) turbine 30；With jet-propelled exhaust nozzle section 32.HP turbines 28 are drivingly coupled to HP compressors 24 by high pressure (HP) axle or rotating shaft 34. LP turbines 30 are drivingly coupled to LP compressors 22 by low pressure (LP) axle or rotating shaft 36.

In addition, for the embodiment of description, fan section 14 includes variablepiston fan 38, and the variablepiston fan 38 has There are the multiple fan blade 40 for being connected in disk 42 in a spaced apart manner.As depicted, fan blade 40 is in generally radial direction Direction R extends outwardly from disk 42.Each restriction leading edge 44 or upstream edge and tip 46 in multiple fan blade 40, tip 46 are limited at the radially outward edge of each respective fans blade 40.Each fan blade 40 can also be operated by means of fan blade 40 Ground is connected in suitable actuating assembly 48 and surrounds pitch axis P relative to disk 42, and the actuating assembly 48 is configured to below The mode of detailed description changes the pitch of fan blade 40.Fan blade 40, disk 42 and actuating assembly 48 can surround longitudinal axis Line 12 is rotated together by the LP axles 36 across power gear-box 50.Power gear-box 50 includes multiple gears, for by LP The rotary speed of axle 36 is gradually lowered to rotary fan speed more efficiently.In addition, for the embodiment of description, variable oar Disk 42 away from fan 38 is covered by rotatable front hub 52, and the rotatable front hub 52 aerodynamically forms profile, to promote Through the air stream of multiple fan blade 40.

Again referring to Fig. 1 demonstration turbofan 10, demonstration fan section 14 also includes ring-type fan housing or outer Cabin 54, ring-type fan housing or outer cabin 54 circumferentially surround at least one of fan 38 and/or core turbogenerator 16 Point.It should be appreciated that cabin 54 may be configured to by multiple export orientation stator blades 56 being circumferentially spaced relative to core turbine Engine 16 supports.Moreover, the downstream section 58 of cabin 54 can extend above the outer portion of core turbogenerator 16, so as to Bypath air circulation road 60 is limited therebetween.

During the operation of turbofan 10, substantial amounts of air 62 is through cabin 54 and/or fan section 14 Relevant inlet 64 enters turbofan 10.When the substantial amounts of air 62 advances across fan blade 40, indicated by arrow 66 The Part I of air is directed or is sent in bypath air circulation road 60, and the Part II of the air indicated by arrow 68 It is directed or is sent in LP compressor 22.Ratio between the Part I 66 of air and the Part II 68 of air is commonly referred to as For by-pass ratio.High pressure (HP) compressor 24 is through in the Part II 68 of air to send and when being sent in burning block 26, Its pressure and then increase, at burning block, the Part II 68 of the air is mixed and burnt with fuel, to provide burning gases 70。

Burning gases 70 are sent across HP turbines 28, here, via the HP turbine stators stator blade 72 for being connected in shell 18 With the continuous levels of the HP turbine rotor blades 74 that are connected in HP axles or rotating shaft 34 heat energy and/or kinetic energy are extracted from burning gases 70 A part, therefore cause HP axles or rotating shaft 34 to rotate, so as to support the operation of HP compressors 24.Then burning gases 70 are sent Through LP turbines 30, here, via the LP turbine stators stator blade 76 for being connected in shell body 18 and being connected in LP axles or rotating shaft 36 The continuous level of LP turbine rotor blades 78 extracts heat energy and kinetic energy from burning gases 70, therefore causes LP axles or rotating shaft 36 to rotate, So as to support the operation of LP compressors 22 and/or the rotation of fan 38.

Burning gases 70 are then sent across the jet-propelled exhaust nozzle section 82 of core turbogenerator 16, to provide Propulsive thrust.Meanwhile it is vented in the Part I 66 of air by the fan nozzle from the turbofan 10 for also providing propulsive thrust When the Part I 66 of air is sent across bypath air circulation road 60 before section 82 is discharged, the Part I 66 of the air Pressure significantly increase.HP turbines 28, LP turbines 30 and jet-propelled exhaust nozzle section 32 at least partially define hot gas road Footpath 84, for making burning gases 70 travel across core turbogenerator 16.

It is to be understood, however, that with reference to the demonstration turbofan 10 described above of figure 1 only as example There is provided.In other example embodiments, demonstration turbofan 10 can have any other suitable construction.For example, In other example embodiments, turbofan 10 can have any other appropriate number of such as rotating shaft or axle, compression Machine, and/or turbine.

Referring now to Figure 2, fan 38 will be described in further detail.Fig. 2 provide Fig. 1 demonstration turbofan 10 from Elevation view after the previous dynasty.For the example embodiment of description, fan 38 includes the individual fan blade 40 in 12 (12).From the sight of load From the point of view of point, such a number of blade enables the span of each fan blade 40 to reduce so that the overall diameter of fan 38 can also reduce (example Such as, it is decreased to about 12 feet in the exemplary embodiments).That is, in other embodiments, fan 38 can have any The suitable number of blade and any suitable diameter.For example, in one suitable embodiment, fan 38 can have at least eight (8) The individual fan blade 40 in individual fan blade 40, at least ten (10), the individual fan blade 40 at least 15 (15) or at least 18 (18) are individual Fan blade 40.

Each fan blade 40 can have suitable aerodynamic profile, including the on the pressure side 100 (figure being for example generally concave And opposite, generally convex suction side 102 and leading edge 104 and opposite trailing edge 106 3).In addition, each fan blade 40 The chord line 105 (Fig. 3) extended between leading edge 104 and trailing edge 26 can be generally limited to.Each fan blade 40 is from interior root end Portion 108 extends to the outside distal tip 110 in footpath, and the interior root end 108 is rotatably coupled to disk 42, the outside distal side end in the footpath The tip 110 is configured to close to blower-casting or cabin 54 for the embodiment of description, for providing relatively small tip therebetween Interval or gap.However, it is to be understood that in other example embodiments, such as when gas-turbine unit is as replacement When being configured to open rotor turbofan or being configured to turboprop, outer distal tip 110 can be indefinite Position is neighbouring any housing or cabin.

Referring now also to Fig. 3 to 5, there is provided the sectional view for the demonstration fan blade 40 in the radial direction R observed.Such as above Discussed, each in multiple fan blade 40 can surround corresponding pitch axis P by blade pitch actuating assembly 48 Rotation.For the embodiment of description, fan blade 40 is each limited relative to the pitch angle 112 of direction of rotation, by arrow 114 The direction of rotation of instruction.Specifically, limited for the embodiment of description, the pitch angle 112 of each corresponding fan blade 40 Between corresponding chord line 105 and direction of rotation 114.By changing pitch angle 112, fan 38 can be manipulated and be used for providing The forward thrust 116 (Fig. 3) of turbofan 10, thrust (Fig. 4) or standby for turbofan 10 is not provided Selection of land provides the deboost 118 (Fig. 5) for turbofan 10.

Specifically, the demonstration fan 38 of description can change the pitch angle 112 of multiple fan blade 40 so that multiple The pitch range of each restriction first and the second pitch range in fan blade 40.Especially for the embodiment of description, the first oar It is configured to generate forward thrust away from scope, and the second pitch range is configured to generate deboost.Pushed away forward for generating First pitch range of power can be substantially in the pitch angle 112 about between zero degree and approximately ninety degrees, such as about Between five degree and about 75 degree, such as in about ten degrees and about between 60 degree.Therefore, as it is used in the present context, The first pitch range for generating forward thrust can also include the propeller pitch angle for being used to not generate thrust of multiple fan blade 40 Degree 112.Alternatively, can be in about zero degree and about minus between 90 degree for generating the second pitch range of deboost, it is all It is such as at about minus five degree and about minus between 75 degree, it is minus between 60 degree such as at about minus ten degree and about.

It is to be understood, however, that in other example embodiments, the first and second pitch models of multiple fan blade 40 Enclosing can be as any other the suitable scope for replacing limiting pitch angle 112.For example, generation forward thrust is to deboost The pitch angle 112 of each corresponding fan blade 40 may depend on the shape of such a fan blade 40 and change.In addition, the first oar Fixed pitch range is can not be away from scope.For example, the pitch angle 112 of each respective fans blade 40 of generation forward thrust It may also depend upon the relative velocity that such as fan 38 and engine 10 are run and change.Moreover, in another example embodiment, the One pitch range can be as the pitch range that the forward thrust in best efficiency ranges is generated instead of blade 40, and the second oar Can be that fan blade 40 still generates forward thrust but less efficient pitch range away from scope.In such a embodiment, fan 38 It or can can not generate deboost.

Now generally with reference to Fig. 6 and 7, describe the blade pitch actuating assembly 48 according to the example embodiment of the disclosure. As mentioned above, each fan blade 40 can rotate relative to disk 42 around pitch axis P.Fan blade 40, disk 42, Longitudinal axis 12 can be surrounded by being rotated together across the LP axles 36 of power gear-box 50 (Fig. 1) with actuating assembly 48.Fan Blade 38 may also include fan shaft 120, and power gear-box is mechanically coupled to disk 42 (see Figure 12, below) by the fan shaft 120.

Actuating assembly 48 generally includes multiple actuation components.Particularly with the embodiment of description, actuating assembly 48 includes Grooming ring 122, multiple chain arms 124 and actuator 126.For the embodiment of description, actuator 126 is that rotating hydraulic actuates Device.However, in other embodiments, actuator 126 can be used as instead of electric actuator (that is, electro-motor).Each fan leaf Piece 40 can be rotatably coupled to disk 42 by corresponding chain arm 124.Specifically, each fan blade 40 can be with rotatable Ground is connected in the first end 128 of corresponding chain arm 124 so that first end 128 and corresponding fan blade 40 can surround Pitch axis P rotates relative to disk 42.At this point, fan blade 40 can be fixedly connected to the of corresponding chain arm 124 One end 128 so that the rotation of chain arm 124 causes fan blade 40 to be rotated relative to disk 42.

The second end 130 of chain arm 124 can be slidably connected to the multiple conduits limited in grooming ring 122 One in 132.For example, the second end 128 can be pivotably coupled to slide unit 134.Slide unit 133 can be by can It is slidably received in the conduit 132 of grooming ring 122.

Grooming ring 122 can rotate around longitudinal centre line 12 relative to disk 42, and operatively couple with actuator 126, Actuator 126 is fixed relative to disk 42.In operation, actuator 126 makes grooming ring 122 be rotated relative to disk 42.In grooming ring During 122 rotation, each in corresponding slide unit 134 moves along corresponding conduit 132, and the angle of corresponding chain arm 124 Spend change in location.When each chain arm 124 rotates, corresponding fan blade 40 also rotates, so that each fan blade 40 surrounds Pitch axis P rotates.

At this point, each pitch angle 112 in the multiple fan blade 40 of the position instruction of grooming ring 122.Therefore, It is each around their corresponding pitch axis P rotations in multiple fan blade 40 by making grooming ring 122 be rotated relative to disk 42 Pitch angle 112 corresponding to going to.Therefore, the first range of movement is limited for the embodiment of description, grooming ring 122, this first Range of movement corresponds to by each the first pitch range limited in multiple fan blade 40.Specifically, grooming ring 122 First range of movement can be the first range of movement relative to disk 42 (and pin assemblies 140, be discussed below).First pitch model Enclose, and therefore therefore the first range of movement of grooming ring 122 may correspond to be used to generate forward thrust (or not producing thrust) Pitch angle 112.For the embodiment of description, first range of movement is presented in figs. 6 and 7.Specifically, the tune in Fig. 6 The position of degree ring 122 can cause fan blade 40 to limit the demonstration pitch angle 112 described in Fig. 3, and the grooming ring in Fig. 7 122 position can cause fan blade 40 to limit the demonstration pitch angle 112 described in Fig. 4.

It is to be understood, however, that what the demonstration actuating assembly 48 described in Fig. 6 and 7 provided only as example.At it In his example embodiment, it is possible to provide any other suitable actuating assembly 48.For example, although Fig. 6 and 7 demonstration actuating assembly 48 Including multiple chain arms 124, but in other example embodiments, actuating assembly 48 can replace chain arm 124, the tooth with gear Wheel construction interacts into one or more matching gears on grooming ring 122.Moreover, although actuating assembly 48 is depicted For rotary actuator, (that is, actuating assembly 48 around axial direction A and longitudinal centre line 12 relative to disk 42 by rotating to change Multiple pitch angles 112 in multiple fan blade 40), but in other example embodiments, actuating assembly 48 can conduct Instead of being configured to electronic or hydraulic linear actuator.By this example embodiment, actuating assembly 48, which can be used as to substitute, includes one Or more such as lower component, the part is configured in axial direction A and moved relative to disk 42, to change multiple fan blade 40 Pitch angle 112.In addition, although the conduit 132 limited in Fig. 6 and 7 demonstration grooming ring 122 is depicted as generally edge Longitudinal centre line 12 extends, but in other example embodiments, conduit 132 can limit curved shape or other shapes, so as to right Each offer in single fan blade 40 is particularly dispatched, for example, to prevent overlapping fan blade 40 in the operation phase Between knock each other.

Refer back to accompanying drawing, it will be appreciated that, the deboost generated during flight can cause to have such a flight Evil influences.Therefore, the actuating assembly 48 of description also includes following mechanism, and the mechanism is used to ensure not adopting vigorous measures to permit Perhaps grooming ring 122 is not moved more than the first range of movement in the case of such a movement.Specifically, the demonstration grooming ring of description 122 limit multiple paths 136.The demonstration path 136 of description generally circumferentially direction C extends, and each limit length 138. For the embodiment of description, grooming ring 122 allows range of movement during the length 138 of each path 136 corresponds to flight forward (that is, multiple fan blade 40 allow pitch range) during flight forward.Particularly with the embodiment of description, each path 136 length 138 represents the first pitch range of multiple fan blade 40.Therefore, for the embodiment of description, each path 136 Length 138 can represent following pitch range, in the pitch range, multiple fan blade 40 be configured for generation pushes away forward Power does not generate thrust.However, in other embodiments, the first pitch range of fan blade 40 can correspond to as replacing Any other suitable pitch range, as discussed above.

There is provided pin assemblies 140 for engagement path 136 in it is each, with ensure ought such as deboost it is undesirable When, grooming ring 122 is maintained in the first range of movement.Particularly, although embodiment for description, provided with multiple pin assemblies 140, the path 136 of wherein respective amount is limited in demonstration grooming ring 122, but in other example embodiments, it is possible to provide Any other appropriate number of pin assemblies 140 and path 136.

Referring now again to Fig. 8 and 9, there is provided according to feature, the sectional view of the pin assemblies 140 of example embodiment.It is specific and Speech, Fig. 8 provides feature, the sectional view of the demonstration pin assemblies 140 in the position that Fig. 6 describes of grooming ring 122, and Fig. 9 is provided Grooming ring 122 is in feature, the sectional view of the demonstration pin assemblies 140 of the position of Fig. 7 descriptions.

The demonstration pin assemblies 140 of description generally include pin 142 and pin main body 144.Pin 142 can be in pin main body 144 It is moved linearly by between first position (Fig. 6 to 9) and the second place (Figure 10 and 11, be discussed below).As shown, when When pin 142 is in first position, pin 142 is positioned at least partially in the respective channels 136 limited by grooming ring 122.When extremely When being partially positioned in the respective channels 136 limited by grooming ring 122, pin 142 stops grooming ring 122 relative to pin 142 More than the movement of the scope limited by the length 138 of path 136.Therefore, for the embodiment of description, the demonstration of pin assemblies 140 Pin 142 (when in said first position) stops the movement outside the first range of movement of grooming ring 122 of grooming ring 122, so as to Prevent multiple fan blade 40 from being limited to the pitch angle 112 outside the first pitch range, this can be for generate forward thrust or The scope of the pitch angle 112 of thrust is not generated.

However, such as stated before, at least some of situation, fan blade 40 is moved to outside the first pitch range Such as to generate a large amount of deboosts using fan 38 it is probably beneficial.Therefore, with reference now to Figure 10 and 11, for making wind The construction that fan leaf 40 is moved to outside the first pitch range provides the view of actuating assembly 48 and pin assemblies 140.Specifically, adjust Degree ring 122 further defines the second range of movement relative to disk 42 and pin assemblies 140.Second range of movement of grooming ring 122 is corresponding Each the second pitch range limited in by multiple fan blade 40.For the embodiment of description, multiple fan blade 40 The second pitch range be multiple fan blade 40 be configured to generate deboost pitch angle 112 scope.However, In other embodiment, the second pitch range can correspond to the oar outside the best efficiency ranges of fan blade 40 in addition or alternatively The scope of elongation degree 112.

However, as shown, the second range of movement of grooming ring 122 is in the path 136 by being limited in grooming ring 122 Length 138 provide permissible range outside.Therefore, in order to enter in the second range of movement, the pin 142 of pin assemblies 140 must move Move to the second place so that pin 142 is not positioned at least partially in the path 136 limited by grooming ring 122, and is not therefore hindered Keep off such a movement.Therefore, including retraction system 146 is for being selectively engaged pin 142, and pin 142 is moved from first position Move to the second place.For the embodiment of description, retraction system 146 is the hydraulic retraction system using hydraulic pressure, to work as quilt Pin 142 is optionally set to be moved to the second place from first position during startup.

For example, specifically with reference to figure 11, and referring now also to provide the side of actuating assembly 48 of demonstrating, sectional view figure 12, demonstration pin assemblies 140 include the top chamber 148 limited by pin main body 144.The top chamber 148 of pin main body 144 fluidly connects In hydraulic fluid circuits 150.For the embodiment of description, hydraulic fluid circuits 150 are fluidly coupled to turbofan 10 excretion circuit 154, when installing the wheel of aircraft of turbofan 10 on the ground, the excretion circuit 154 can It is pressurized.However, in other example embodiments, hydraulic fluid circuits 150 can be used as instead of with turbofan 10 The separated hydraulic fluid circuits that independently start of other actuator undergrounds 156 (including for example draining circuit 154).

When starting retraction system 146 with retraction pin 142, i.e. when the pin 142 is moved to the second place, hydraulic fluid circuits 150 pairs of top chambers 148 provide pressurized hydraulic fluid.The pressure in fluid increase top chamber 148 in top chamber 148, and substantially On in the radial direction R promote 142 inwardly towards the second place.More specifically, hydraulic fluid in the radial direction R promotes 142 inwardly On annular flange 152 so that pin 142 is moved to the second place.

After being selectively engaged pin 142 and pin 142 is moved to the second place, pin 142 can by with retraction system 146 disengagements and rotary fan 38 and move back into first position.Centrifugal force will be such that pin 142 moves back in first position. Especially, when not actuated retraction system 146, in the absence of shift pin 142 in the second place onto biasing force.Therefore, when not opening During dynamic retraction system 146, the centrifugal force using minimum makes pin 142 be moved to first position so that can be by with relatively low Speed rotary fan 38 and pin 142 is moved to first position.

It is to be understood, however, that in other example embodiments, it is possible to provide any other suitable retraction system 146. For example, in other example embodiments, retraction system 146 can be power driven system, and the power driven system is using electric actuator to incite somebody to action Pin 142 is moved to the second place from first position.Alternatively, retraction system 146 can be electromagnetism retraction system.In addition, another In example embodiment, retraction system 146 can be pneumatic retraction system.However, it should be understood that the although demonstration pin bank described Part 140 includes pin 142, and the pin 142 linearly extends between the first location and the second location, but in other example embodiments In, pin 142, which can be used as, to be replaced pivoting or rotating between the first location and the second location.In addition, although demonstrate pin 142 generally Columnar shape is limited, but in other example embodiments, the pin 142 of pin assemblies 140, which can limit, allows pin 142 first and the Any other the suitable shape moved between two positions.

Moreover, in another example embodiment, actuating assembly 48, which can be used as, replaces having pin assemblies 140, the pin assemblies 140 Interacted with any other suitable actuation component.For example, in other example embodiments, the chain of actuating assembly 48 of demonstrating One or more in arm 124 are limited to path therein.In such a example embodiment, the pin of pin assemblies may be configured to Interacted with such a path, the movement of the scope limited by path is exceeded to stop chain arm 124 relative to pin, for example, with With almost identical mode described above.

Referring now specifically to Figure 12, it should be appreciated that pin assemblies 140 attach to fan shaft 120 (its for example can by across The LP axles 36 of power gear-box 50 drive), and the pin main body 144 of pin assemblies 140 is fixed relative to fan shaft 120.However, at it In his example embodiment, pin main body 144 can be any relative to being rotated together with disk 42 and multiple fan blade 40 as replacing Other suitable parts are fixed.

The fan for gas-turbine unit with the actuating assembly according to disclosure example embodiment can provide more Individual fan blade will not be for example moved to during flight for generate deboost pitch range in guarantee, even if for example The loss of system pressure.In addition, it is used for gas-turbine unit with the actuating assembly according to disclosure example embodiment After fan can allow after wheel contacts ground, or deboost is probably desirable some other conditions behind Make security feature disengagement immediately.In addition, it is used for gas turbine with the actuating assembly according to disclosure example embodiment The fan of engine can allow when to engage security feature during relatively low speed rotary fan.

This written explanation, to disclose the present invention including preferred forms, and also makes any this area skill using example Art personnel can put into practice the present invention, including manufacture and using any equipment or system and the method that performs any merging.This hair Bright patentable scope is defined by the claims, and may include other examples expected by those skilled in the art. If these other examples include the indiscriminate structural detail of literal language with claim, or if they include and right It is required that equivalent structural elements of the literal language without marked difference, then they are within the scope of the claims.

Claims

1. a kind of variablepiston fan (38) for gas-turbine unit, the variablepiston fan (38) includes：

Multiple fan blade (40), it is rotatably coupled to disk (42), each restriction in the multiple fan blade (40) Pitch；With

Actuating assembly, it is used to change each pitch in the multiple fan blade (40), and the actuating assembly includes：

Actuation component, it is operably connected at least one and restriction path (136) in the multiple fan blade (40)； With

Sell (142), it can be moved between the first location and the second location, and in the first position, the pin (142) is extremely Partially it is positioned in the path (136) being limited in the actuation component, described in when in the first position Pin (142) stops that the actuation component exceeds the movement of the scope limited by the path (136) relative to the pin (142)； With

Retraction system (146), it is used to be selectively engaged the pin (142) and makes the pin (142) from the first position It is moved to the second place；

Wherein, the actuation component is chain arm (124), wherein, the actuating assembly also includes multiple chain arms (124), and Wherein, each chain arm (124) is operatively coupled to one in the multiple fan blade (40).

2. variablepiston fan (38) according to claim 1, wherein, the actuation component is can be relative to the disk (42) grooming ring (122) of rotation.

3. variablepiston fan (38) according to claim 2, wherein, it is limited to described in the grooming ring (122) Generally circumferentially direction extends path (136).

4. variablepiston fan (38) according to claim 1, wherein, the path（136）Limit length, wherein, institute The length for stating path (136) represents the first pitch range of the multiple fan blade (40).

5. variablepiston fan (38) according to claim 4, wherein, the multiple fan blade (40) further defines second Pitch range, wherein, when the pin (142) is in the second place, the actuation component is limited than the path (136) The big range of movement relative to the pin (142) of length, and wherein, the range of movement of the increase of the actuation component is corresponding In the second pitch range of the multiple fan blade (40).

6. variablepiston fan (38) according to claim 1, wherein, the actuating assembly also includes pin main body (144), Wherein, the pin (142) can be mobile relative to the pin main body (144) between the first position and the second place.

7. variablepiston fan (38) according to claim 6, wherein, the pin (142) is in the first position and It is moved linearly by between two positions relative to the pin main body (144).

8. variablepiston fan (38) according to claim 6, wherein, the retraction system (146) is hydraulic retraction system Unite (146), the hydraulic retraction system (146) optionally makes the pin (142) be moved to described second using hydraulic pressure Position.

9. variablepiston fan (38) according to claim 6, wherein, the multiple fan blade (40) can pass through wind Fan axle and rotate, and wherein, the pin main body (144) is fixed relative to the fan shaft.

10. a kind of variablepiston fan (38) for gas-turbine unit, the variablepiston fan (38) includes：

Wherein, the path（136）Limit length, wherein, the length of the path (136) represents the multiple fan blade (40) the first pitch range, the multiple fan blade (40) further define the second pitch range, wherein, when the pin (142) During in the second place, the actuation component limits bigger than the length of the path (136) relative to the pin (142) Range of movement, and wherein, the range of movement of the increase of the actuation component corresponds to the of the multiple fan blade (40) Two pitch ranges.